Accession Number:

ADA071573

Title:

Aerodynamic Heating in the Fin Interaction Region of Generalized Missile Shapes at Mach 6 (Modular Missile Test Program)

Descriptive Note:

Final rept. Jul 74-Apr 79

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1979-05-01

Pagination or Media Count:

171.0

Abstract:

The characteristics of three-dimensional shock wave turbulent boundary layer interactions are investigated for a finned ogive-cylinder configuration. An extensive experimental program was conducted in the AEDCVKF Tunnel B at Mach 6 and a unit Reynolds number of 4.9 million per foot. The model was an ogive-cylinder 50 inches long and 8.5 inches in diameter with fins mounted at model station 42. Heat transfer data were taken on the cylinder and on the fin surface in the interaction region of swept and unswept fins sealed to the cylinder and for a swept fin mounted on a torque tube. The objective of this effort was to correlate the peak interaction heating produced by missile control surfaces through extension of more geometrically simple concepts. Previous work reported for these more simple geometries is extended through this report to more practical configurations. The principle correlating parameter must be based on local flow properties which may be obtained from inviscid flow field computer program solutions. Extensive flow field probing of the shock layer on the ogive-cylinder alone was conducted and the results are shown to agree well with inviscid solutions.

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE